Attitude Tracking Control of Rigid Spacecraft Based on Fully Actuated System Models

This paper proposes a direct parametric design method for the attitude tracking control of a rigid spacecraft to address the problem of satellite attitude control performance affected by external disturbance. Firstly, the fully-actuated system model for attitude tracking control of a rigid spacecraft is established using quaternions. An extended state observer (ESO) is then developed to handle the influence caused by external disturbances. Then, a controller is designed using the direct parametric method to achieve high-accuracy attitude tracking control of the rigid spacecraft and reach the desired position. Finally, a numerical example involving a rigid spacecraft is presented to demonstrate the effectiveness of the proposed approach in achieving the design objective and exhibiting good control performance.